GB814380A - Power plant incorporating a dynamic compressor - Google Patents
Power plant incorporating a dynamic compressorInfo
- Publication number
- GB814380A GB814380A GB3260454A GB3260454A GB814380A GB 814380 A GB814380 A GB 814380A GB 3260454 A GB3260454 A GB 3260454A GB 3260454 A GB3260454 A GB 3260454A GB 814380 A GB814380 A GB 814380A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzles
- compressor
- fuel
- discharge
- oxidant
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000007789 gas Substances 0.000 abstract 6
- 239000000446 fuel Substances 0.000 abstract 4
- 239000007800 oxidant agent Substances 0.000 abstract 3
- 230000001590 oxidative Effects 0.000 abstract 3
- 238000002485 combustion reaction Methods 0.000 abstract 2
- 239000012530 fluid Substances 0.000 abstract 1
- 230000001141 propulsive Effects 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
814,380. Jet propulsion plant; gas turbine plant. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Nov. 2, 1955 [Nov. 10, 1954], No. 32604/54. Class 110 (3). In a jet propulsion plant, the compressor is driven by the tangential discharge of highvelocity gas through nozzles mounted at the circumference of the compressor rotor. The gas is produced by an oxidant and a fuel in a combustion chamber and is passed radially outwards to the nozzles from which it flows to a secondary combustion chamber and is discharged, as a propulsive jet, through a variable area outlet. In a second embodiment, not shown, the compressor is driven both by the nozzles and by a turbine driven by the nozzle discharge gases. As shown, the gases formed in chamber 16 by the combination of fuel and oxidant flow radially outwards through passages 10 in the rotor 9 to the discharge nozzles 23 set at an angle to the rotor plane. 9 is caused to rotate by the tangential component of the discharge and thus drives the compressor 8 set in the air intake 1. The nozzle discharge gases when mixed with the compressed air stream continue to burn in chamber 27. Release is effected by nozzles 29 through which fuel or oxidant may be injected. The outlet area is adjustable by members 31. Preheating of the fuel may be effected by its passage through a heat exchanger to which heat is supplied by a fluid which flows through a circuit adjacent the aircraft surface and thus absorbs heat generated by air friction. Specifications 749,009 and 808,833 are referred to.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB814380A true GB814380A (en) | 1959-06-03 |
Family
ID=1743087
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3260454A Expired GB814380A (en) | 1954-11-10 | Power plant incorporating a dynamic compressor |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB814380A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2410737A1 (en) * | 1977-12-01 | 1979-06-29 | United Technologies Corp | BURNER FOR GAS TURBINE |
| GB2176246A (en) * | 1985-05-31 | 1986-12-17 | Gen Electric | Rotor stage in a turbomachine |
| DE19740228A1 (en) * | 1997-09-12 | 1999-03-18 | Bmw Rolls Royce Gmbh | Turbofan aircraft engine |
| EP2532857A1 (en) * | 2011-06-06 | 2012-12-12 | United Technologies Corporation | Turbomachine assembly with combustors having different flow directions and corresponding operating method |
-
1954
- 1954-11-10 GB GB3260454A patent/GB814380A/en not_active Expired
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2410737A1 (en) * | 1977-12-01 | 1979-06-29 | United Technologies Corp | BURNER FOR GAS TURBINE |
| GB2176246A (en) * | 1985-05-31 | 1986-12-17 | Gen Electric | Rotor stage in a turbomachine |
| GB2176246B (en) * | 1985-05-31 | 1989-10-25 | Gen Electric | Improvements in turbomachines |
| DE19740228A1 (en) * | 1997-09-12 | 1999-03-18 | Bmw Rolls Royce Gmbh | Turbofan aircraft engine |
| US6260352B1 (en) | 1997-09-12 | 2001-07-17 | Rolls-Royce Deutschland Ltd & Co Kg | Turbofan aircraft engine |
| EP2532857A1 (en) * | 2011-06-06 | 2012-12-12 | United Technologies Corporation | Turbomachine assembly with combustors having different flow directions and corresponding operating method |
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